US20060006212A1 - Method of brazing composite material parts sealed with a silicon-based composition - Google Patents

Method of brazing composite material parts sealed with a silicon-based composition Download PDF

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Publication number
US20060006212A1
US20060006212A1 US11/157,398 US15739805A US2006006212A1 US 20060006212 A1 US20060006212 A1 US 20060006212A1 US 15739805 A US15739805 A US 15739805A US 2006006212 A1 US2006006212 A1 US 2006006212A1
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parts
brazing
silicon
ceramic material
composition
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Jacques Thebault
Clement Bouquet
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Safran Ceramics SA
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SNECMA Propulsion Solide SA
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Publication of US20060006212A1 publication Critical patent/US20060006212A1/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/19—Soldering, e.g. brazing, or unsoldering taking account of the properties of the materials to be soldered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/08—Soldering by means of dipping in molten solder
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
    • C04B37/003—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of a combination of materials selected from glass, or ceramic material with metals, metal oxides or metal salts
    • C04B37/005—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of a combination of materials selected from glass, or ceramic material with metals, metal oxides or metal salts consisting of glass or ceramic material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/16—Composite materials, e.g. fibre reinforced
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/30—Constituents and secondary phases not being of a fibrous nature
    • C04B2235/42—Non metallic elements added as constituents or additives, e.g. sulfur, phosphor, selenium or tellurium
    • C04B2235/428—Silicon
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
    • C04B2235/616—Liquid infiltration of green bodies or pre-forms
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
    • C04B2237/04—Ceramic interlayers
    • C04B2237/08—Non-oxidic interlayers
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
    • C04B2237/04—Ceramic interlayers
    • C04B2237/08—Non-oxidic interlayers
    • C04B2237/083—Carbide interlayers, e.g. silicon carbide interlayers
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
    • C04B2237/16—Silicon interlayers
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C04B2237/365—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • C04B2237/385—Carbon or carbon composite
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
    • C04B2237/52—Pre-treatment of the joining surfaces, e.g. cleaning, machining
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
    • C04B2237/55—Pre-treatments of a coated or not coated substrate other than oxidation treatment in order to form an active joining layer
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
    • C04B2237/59—Aspects relating to the structure of the interlayer
    • C04B2237/592—Aspects relating to the structure of the interlayer whereby the interlayer is not continuous, e.g. not the whole surface of the smallest substrate is covered by the interlayer
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
    • C04B2237/72—Forming laminates or joined articles comprising at least two interlayers directly next to each other
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • Y10T156/1062—Prior to assembly

Definitions

  • the invention relates to assembling thermostructural composite material parts by brazing.
  • thermostructural composite material Structures made of thermostructural composite material and having complex shapes are difficult to make directly as single parts. It is generally preferred to build up a structure from elements that are of simple shape and that are assembled together, in particular by brazing.
  • brazing is an assembly technique which consists in causing a metal-based composition to melt between the parts that are to be assembled together.
  • the main advantage of brazing is that it enables the parts that are to be assembled together to be assembled without melting the materials constituting said parts, unlike welding.
  • alloys of silicon+metallic silicides, of silicon+optionally alloyed germanium, and also metallic compositions known under the trade names Cusil-ABA®, Ticusil®, Incusil®, and Brasic® are to be found alloys of silicon+metallic silicides, of silicon+optionally alloyed germanium, and also metallic compositions known under the trade names Cusil-ABA®, Ticusil®, Incusil®, and Brasic®.
  • Thermostructural composite materials are known for their good mechanical properties and their ability to conserve these properties at high temperature. They comprise composite materials constituted by reinforcement of refractory fibers densified by a matrix that is also refractory.
  • such materials include carbon-carbon (C/C) composites (reinforcement of carbon fibers densified by a matrix of carbon), and ceramic matrix composite (CMC) materials such as C/SiC composites (reinforcement made of carbon fibers and matrix made of silicon carbide), SiC/SiC composites (both fibers and matrix made of silicon carbide), C/C—SiC composites (reinforcement of carbon fibers and matrix comprising a carbon phase, generally closest to the fibers, and also a silicon carbide phase), C/C composites that have been silicided with gaseous SiO, liquid Si, etc.
  • thermostructural composite material The usual methods for obtaining parts of made of thermostructural composite material include the liquid technique and the gas technique.
  • the liquid technique consists in making a fiber preform having substantially the shape of the part that is to be made, and that is to constitute the reinforcement of the composite material, and in impregnating said preform with a liquid composition containing a precursor for the matrix material.
  • the precursor is generally in the form of a polymer, such as a resin, possibly diluted in a solvent.
  • the precursor is transformed into the refractory phase by heat treatment, after eliminating any solvent, and after curing the polymer. A plurality of successive impregnation cycles can be performed in order to achieve a desired degree of densification.
  • liquid precursors of carbon can be resins having a relatively high coke content, such as phenolic resins
  • liquid precursors of ceramics, in particular of SiC can be resins of the polycarbosilane type (PCS) or of the polytitanocarbosilane (PTCS) type or of the polysilazane (PSZ) type.
  • PCS polycarbosilane type
  • PTCS polytitanocarbosilane
  • PSZ polysilazane
  • the gas technique consists in chemical vapor infiltration.
  • the fiber preform corresponding to a part that is to be made is placed in an oven into which a reaction gas is admitted.
  • the pressure and the temperature that exist inside the oven and the composition of the gas are selected in such a manner as to enable the gas to diffuse within the pores of the preform in order to form the matrix therein by a solid material being deposited in contact with the fibers as a result of a component of the gas decomposing or as a result of a reaction between a plurality of components of the gas.
  • gaseous precursors of carbon may be hydrocarbons that give carbon by cracking, e.g. methane
  • a gaseous precursor of ceramic, in particular SiC may be methyltricholorosilane (MTS) which gives SiC by the MTS decomposing (possibly in the presence of hydrogen).
  • MTS methyltricholorosilane
  • parts made of thermostructural composite material always present residual porosity due to the inevitably incomplete nature of the densification of fiber preforms.
  • parts typically, with no particular treatment during densification, parts present pores having a minimum volume content of about 10%.
  • Such porosity represents the presence of pores and/or cracks of greater or smaller dimensions, which communicate with one another, and which open out to the surface of the part.
  • two parts 1 of 2 of thermostructural composite material M are assembled together by brazing by interposing a brazing layer 3 between the surfaces S 1 and S 2 of the parts that are to be untied.
  • a fraction of the brazing composition 3 interposed between the parts 1 and 2 penetrates into pores P in the material via holes that open out into the surfaces of the parts, thereby leaving localized portions 4 that do not have any brazing composition between the two surfaces. This lack of composition leads to defective bonding between the two parts, and consequently to an assembly of degraded quality.
  • a known solution to that problem consists in filling in the pores of the thermostructural composite material parts by siliciding, i.e. by introducing into the material a composition based on molten silicon. That type of siliciding is known in itself and is described in particular in the following documents: FR 2 653 763, U.S. Pat. No. 4,626,516, EP 0 636 700, and FR 03/01871.
  • thermostructural composite materials once silicided in that way, can be considered as being sufficiently impermeable to retain the brazing composition on the surface, the presence of one or more silicide phases within the material leads to another problem.
  • alloys used for brazing purposes contain a significant fraction of metallic components corresponding to transition metals (e.g. Cu, Fe, Ni, Mn, etc.) that react with silicon, leading to the formation of naturally brittle metallic silicides in the bond.
  • transition metals e.g. Cu, Fe, Ni, Mn, etc.
  • brazing composition that is not reactive or that presents controlled reactivity, of the kind implemented in BraSiC® technology
  • brazing temperatures about 1400° C.
  • Direct contact between the silicon of the material and the brazing composition can change the proportions of the brazing composition components by diffusion in the liquid state during brazing, thereby modifying its properties.
  • the invention seeks to provide a method enabling parts of thermostructural composite material to be assembled together by brazing, in which at least the surfaces for putting into contact have been sealed by being impregnated with a silicon-based composition, while avoiding the above-mentioned drawbacks, and in particular preventing any reaction or diffusion between the brazing composition and the silicon present in the material of the parts.
  • this object is achieved by a method in which, after the sealing step and prior to the brazing step, a layer of refractory ceramic material is formed at least on those surfaces of the parts that are to be united, which ceramic material is not reactive with silicon at brazing temperature.
  • a layer of refractory ceramic material is formed at least on those surfaces of the parts that are to be united, which ceramic material is not reactive with silicon at brazing temperature.
  • Such a material may be selected in particular from ceramics that are derivatives of silicon, such as silicon nitride (Si 3 N 4 ) or silicon carbide (SiC).
  • the brazing composition need not come into contact with the silicon or other elements present in the material, since a layer of refractory ceramic is protecting the surface of the material to be brazed.
  • the ceramic e.g. silicon carbide
  • the ceramic withstands corrosion well, so in the event of the bond being reworked or repaired, it is possible to attack the brazing composition with corrosive chemicals while not damaging the material of the parts.
  • the ceramic layer may be formed by chemical vapor deposition or by chemical gas infiltration.
  • the surface of the ceramic layer formed on the surfaces of the parts can be lapped prior to brazing.
  • the mean thickness of the ceramic layer preferably lies in the range 1 micrometer ( ⁇ m) to 100 ⁇ m, being about 50 ⁇ m, for example.
  • the brazing composition used is preferably based on a metal that is not reactive or that presents controlled reactivity relative to the ceramic which covers the surfaces of the parts to be united.
  • an antiwetting agent is applied to those portions of the parts that are to be brazed together so that the brazing composition wets only those surface portions that are to be assembled together.
  • the liquid brazing composition is transported by capillarity to a position between the parts to be united by means of a wick, e.g. constituted by carbon fibers, in order to convey the brazing composition by capillarity between the two parts that are to be united.
  • a wick e.g. constituted by carbon fibers
  • FIG. 1 is a highly diagrammatic view of the result obtained when brazing together two porous thermostructural composite material parts;
  • FIG. 2 is a flow chart showing the successive steps of an implementation of a method of the invention
  • FIG. 3 is a diagram showing a portion of a thermostructural composite material part sealed by siliciding and after a layer of silicon carbide has been deposited on its surface;
  • FIG. 4 is a diagram of the same portion as shown in FIG. 3 , after the layer of silicon carbide has been lapped;
  • FIG. 5 shows how brazing can be performed between two parts while using a capillary wick
  • FIG. 6 is a diagram showing the structure that is obtained after brazing together two parts in accordance with a method of the invention.
  • the brazing assembly method of the present invention applies to any type of silicided thermostructural composite material, i.e. to any material comprising refractory fiber reinforcement densified by a matrix that is also refractory, such as C/C materials, or CMC materials, and in particular C/SiC, SiC/SiC, C/C—SiC, etc. materials.
  • an implementation of a method in accordance with the invention for brazing together two parts made of thermostructural composite material that have been sealed by siliciding comprises the following steps.
  • a first step (step 10 ) consists in sealing the thermostructural composite material of the parts, at least on those surfaces that are to be put together, filling in the pores by impregnating them with a composition based on molten silicon.
  • the composition based on silicon may be constituted by silicon or by a silicon alloy (e.g. SiGe), and at least one other material selected in particular from: iron, cobalt, titanium, zirconium, molybdenum, vanadium, carbon, and boron.
  • Impregnating thermostructural composite materials with a silicon-based composition is a technique that is known in itself, and it is described in particular in the following documents: FR 2 653 763, U.S. Pat. No. 4,626,516, EP 0 636 700, and FR 03/01871.
  • the second step (step 11 ) consists in preparing these surfaces of the two parts that are to be brought together. For this purpose, the contact surfaces of the parts are machined so as to adapt the shape of the docking plane between the two parts.
  • a refractory ceramic layer is deposited on at least one of the surfaces that is to be brazed (step 12 ).
  • the refractory ceramic is selected to be a material that is not reactive with silicon at the brazing temperature.
  • any ceramic corresponding to a derivative of silicon, such as Si 3 N 4 or SiC can be used to protect the surfaces of parts that are to be brazed together.
  • SiC is deposited. This deposition may be performed by chemical vapor deposition (CVD) or by chemical vapor infiltration (CVI).
  • deposition takes place in an oven into which a gaseous precursor of silicon carbide, such as methyltrichlorosilane (MTS) is admitted so as to give silicon carbide by the MTS decomposing, possibly in the presence of gaseous hydrogen (H 2 ).
  • a gaseous precursor of silicon carbide such as methyltrichlorosilane (MTS)
  • MTS methyltrichlorosilane
  • H 2 gaseous hydrogen
  • FIG. 3 which shows a fraction of a part 20 of thermostructural composite material M in which the pores have been filled in, e.g. by being impregnated with a molten composition based on silicon 21 , the surface S 20 of the part 20 that is to be brazed to the corresponding surface of another part is covered in a layer of silicon carbide 22 .
  • microrelief 222 surface nodules
  • a layer of carbide is obtained that is substantially plane, preferably presenting mean thickness e lying in the range 10 ⁇ m to 100 ⁇ m, being about 50 ⁇ m, for example.
  • Such a thickness is obtained by controlling the quality of ceramic, in this case SiC, that is deposited, while also taking account of lapping, if any.
  • the brazing operation comprises two main steps, namely interposing a brazing composition between the surfaces of the part that are to be united one against the other (step 14 ), and heat treatment (step 15 ) that corresponds to raising the temperature above the melting temperature of the brazing composition.
  • the composition may be deposited directly on the surfaces that are to be united.
  • the composition may be conveyed between the parts by capillarity.
  • a “dry” (i.e. non-impregnated) wick 50 e.g. of drain-forming carbon fibers, is interposed between two parts 20 and 30 of thermostructural composite material M having respective surfaces S 20 and S 30 covered in silicon carbide layers 22 and 32 .
  • One end of the wick is immersed in a crucible 60 containing a brazing composition 61 . Thereafter, the temperature is raised until the brazing composition 61 becomes liquid, whereupon it is sucked by capillarity along the wick 50 and distributed over the entire area for brazing between the two parts where they are in contact with the wick.
  • this provides a joint 40 of brazing composition between the two parts 20 and 30 , serving to bond them together. Since, in accordance with the present invention, the surfaces S 20 and S 30 respectively of the parts 20 and 30 are covered in layers of silicon carbide 22 and 32 prior to brazing, there is no direct contact between the brazing composition and the silicon 21 , 31 present at the surfaces of the parts 20 and 30 .
  • an antiwetting agent may be deposited on those zones of the parts that are not to be brazed so as to control the flow of brazing composition so that it wets only those zones of the parts that are to be brazed.
  • the antiwetting agent used may be boron nitride (BN) prepared in the form of an aerosol spray, or the so-called “Stop-Off” products such as the antiwetting agent Stopyt® sold by the supplier Wesgo Metals, or Nicrobraz® products sold by the supplier Wall Colmonoy Limited.
  • Such an antiwetting agent may be used, for example, when fabricating heat exchangers such as those used in the walls of the diverging portion of a thruster nozzle that is cooled by fluid circulation.
  • That type of heat exchanger can be obtained by brazing together two panels of thermostructural composite material, as described in document FR 03/01039, with at least one of the panels having grooves to form fluid circulation channels.
  • an antiwetting agent Prior to the brazing operation, an antiwetting agent is placed on those zones of the panels that are not to be brazed together, e.g. the grooves.
  • the brazing composition can then be deposited in approximate manner over the entire area of the faces to be assembled together, with the composition subsequently migrating onto those zones that are not covered in the antiwetting agent.
  • the antiwetting agent can itself be removed by circulating an acid or any other agent, depending on the indications given by the supplier of the antiwetting agent.
  • the brazing composition is selected in particular as a function of its compatibility with silicon carbide, i.e. it is preferable to select a composition that is not reactive or that presents controlled reactivity with silicon carbide.
  • compositions based on silicon such as those described in European patent application EP 0 806 402 or U.S. Pat. No. 5,975,407, alloys of silicon+metallic silicides, of silicon+optionally alloyed germanium, and metallic compositions known under the following trade names: Cusil-ABA®, Ticusil®, Incusil®, or Brasic®.
  • the method of the invention enables silicided thermostructural composite material parts to be brazed together without any risk of interaction and/or diffusion between the brazing composition and the silicon present in the material. This ensures that a good quality bond is formed between the parts.
  • the refractory ceramic coating enables the material of the parts to be surface protected against oxidation, while leaving no apparent silicon. Furthermore, when the ceramic deposited on the surface of such a part withstands higher temperatures than silicon, it is possible to use brazing compositions having melting temperatures that are higher than is possible when the silicon is itself directly exposed at the surface of the part.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Products (AREA)
  • Laminated Bodies (AREA)
US11/157,398 2004-06-24 2005-06-21 Method of brazing composite material parts sealed with a silicon-based composition Abandoned US20060006212A1 (en)

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Application Number Priority Date Filing Date Title
FR0406892A FR2872072B1 (fr) 2004-06-24 2004-06-24 Procede de brasage de pieces en materiau composite thermostructural siliciure
FR0406892 2004-06-24

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US11/630,577 Abandoned US20080190552A1 (en) 2004-06-24 2005-06-22 Method For Soldering Composite Material Parts

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AT (2) AT502103B8 (no)
DE (2) DE102005025071B4 (no)
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KR101050538B1 (ko) * 2009-06-16 2011-07-20 (주)피티앤케이 무선 전력 충전 시스템 및 그 충전 방법
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FR2872072B1 (fr) 2006-09-29
AT502103B1 (de) 2007-05-15
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GB2415401A (en) 2005-12-28
US20080190552A1 (en) 2008-08-14
GB0511696D0 (en) 2005-07-13
NO340214B1 (no) 2017-03-20
DE102005025071A1 (de) 2006-01-12
EP1786586A1 (fr) 2007-05-23
NO340661B1 (no) 2017-05-29
KR20060046480A (ko) 2006-05-17
WO2006010814A1 (fr) 2006-02-02
CN100525979C (zh) 2009-08-12
CN1712167A (zh) 2005-12-28
DE102005025071B4 (de) 2022-11-17
NO20070438L (no) 2007-01-23
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ITTO20050443A1 (it) 2005-12-25
JP4991529B2 (ja) 2012-08-01
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GB2415401B (en) 2008-12-17
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